Environmental control system for an aircraft

Abstract

An environmental control system of an aircraft includes a compressing device having a compressor configured to receive a first flow of a medium and a turbine configured to receive the first flow of the medium and a distinct second flow of the medium. A dehumidification system is arranged in fluid communication with the turbine. A valve is configured to divert the second flow around the turbine and an inlet port is arranged in fluid communication with the compressor, the turbine, and the dehumidification system.

What is claimed is: 
     
       1. An environmental control system of an aircraft comprising:
 a compressing device including:
 a turbine configured to receive a first flow of medium; and 
 a compressor configured to receive a second flow of medium a distinct from the first flow; 
 
 a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, wherein the at least one heat exchanger is fluidly connected to the compressor and the turbine, wherein the second flow output from the at least one heat exchanger is provided directly to an inlet of the compressor; 
 a dehumidification system in fluid communication with the turbine; 
 a bypass valve configured to divert the first flow around the turbine; and 
 an inlet port arranged in fluid communication with the compressor, the turbine, and the dehumidification system. 
 
     
     
       2. The environmental control system of  claim 1 , wherein the medium is separated into the first flow and the second flow downstream from the at least one heat exchanger. 
     
     
       3. The environmental control system of  claim 1 , wherein the compressing device includes a fan operably coupled to the compressor and the turbine via a shaft, the fan being arranged in fluid communication with the ram air circuit. 
     
     
       4. The environmental control system of  claim 1 , wherein a mixture of the first flow and the second flow is provided to a load, and the bypass valve is operable to control a temperature of the mixture of the first flow and the second flow provided to the load. 
     
     
       5. The environmental control system of  claim 1 , wherein the flow of medium is bleed air. 
     
     
       6. The environmental control system of  claim 5 , wherein the bleed air is provided from at least one of an engine and an auxiliary power unit of the aircraft. 
     
     
       7. The environmental control system of  claim 1 , wherein a third flow of the medium supplied via the inlet port is separated into the first flow and the second flow within the environmental control system, the first flow being supplied to the turbine and the second flow being supplied to the compressor. 
     
     
       8. The environmental control system of  claim 7 , wherein the turbine has a first inlet and a second inlet, the first inlet receiving the first flow and the second inlet receiving the second flow. 
     
     
       9. The environmental control system of  claim 8 , wherein the first flow mixes with the second flow at an exit of the turbine. 
     
     
       10. The environmental control system of  claim 8 , wherein the dehumidification system is positioned upstream from the first inlet of the turbine. 
     
     
       11. The environmental control system of  claim 1 , wherein the environmental control system is operable in a plurality of modes including a first mode and a second mode. 
     
     
       12. The environmental control system of  claim 11 , wherein the environmental control system is operable in the first mode when an ambient temperature is at or above a design point of the environmental control system. 
     
     
       13. The environmental control system of  claim 11 , wherein the environmental control system is operable in the second mode when an ambient temperature is below a design point of the environmental control system. 
     
     
       14. The environmental control system of  claim 11 , wherein the bypass valve is in a closed position during operation in the first mode and the bypass valve is in an open position during operation in the second mode. 
     
     
       15. A method of operating an environmental control system of an aircraft comprising:
 providing a flow of medium to the environmental control system including a compressor and a turbine; 
 separating the flow of medium into a first portion and a second portion downstream of a heat exchanger of a ram air circuit; and 
 providing the second portion to the compressor and the turbine sequentially, wherein the second portion is provided from an outlet of the heat exchanger directly to an inlet of the compressor; 
 wherein in a first mode of operation, the first portion and the second portion of the flow of medium mix within or at an outlet of the turbine and 
 in a second mode of operation the first portion bypasses the turbine such that the first portion and the second portion of the flow of medium mix downstream from the turbine. 
 
     
     
       16. The method of  claim 15 , wherein the environmental control system is transformed from the first mode of operation to the second mode of operation by opening a bypass valve. 
     
     
       17. The method of  claim 15 , wherein a temperature of the mixture of the first portion and the second portion generated in the first mode of operation is cooler than a temperature of the mixture of the first portion and the second portion generated in the second mode of operation. 
     
     
       18. The method of  claim 15 , wherein the flow of medium provided to the environmental control system is bleed air drawn from an engine of the aircraft.